公开(公告)号：US08820090B2

公开(公告)日：2014-09-02

申请号：US13603804

申请日：2012-09-05

Applicant: Ching-Pang Lee ,  Evan C. Landrum ,  Jiping Zhang

Inventor： Ching-Pang Lee ,  Evan C. Landrum ,  Jiping Zhang

IPC: F02C9/00 ,  F02C3/30

CPC classification number: F01D21/00 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18

Abstract: During full load operation of gas turbine engine operation, a valve system is maintained in a closed position to substantially prevent air from passing through a piping system of a shell air recirculation system. Upon initiation of a turn down operation, which is implemented to transition the engine to a turning gear state or a shut down state, the valve system is opened to allow air to pass through the piping system. A blower is operated to extract air through at least one outlet port of the shell air recirculation system from an interior volume of an engine casing portion associated with the combustion section, to convey the extracted air through the piping system, and to inject the air into the interior volume of the engine casing portion through at least one inlet port of the shell air recirculation system to circulate air within the engine casing portion.

Abstract translation: 在燃气轮机发动机运行的满载运行期间，阀系统保持在关闭位置，以基本上防止空气通过壳体空气再循环系统的管道系统。 在开始执行将发动机转换到转向齿轮状态或关闭状态的转向操作时，阀系统被打开以允许空气通过管道系统。 操作鼓风机以通过壳体空气再循环系统的至少一个出口从与燃烧部分相关联的发动机壳体部分的内部空间提取空气，以将提取的空气输送通过管道系统，并将空气注入 发动机壳体部分的内部体积通过壳体空气再循环系统的至少一个入口端口，以使发动机壳体部分内的空气循环。

公开(公告)号：US20140219809A1

公开(公告)日：2014-08-07

申请号：US13760290

申请日：2013-02-06

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/14

CPC classification number: B22C9/10 ,  F01D5/141 ,  F01D5/187

Abstract: A casting core (200) for a twisted gas turbine engine blade, including: an airfoil portion (202) having: an airfoil base end (208), an airfoil tip end (210), a concave side exterior surface (212), a convex side exterior surface (214), a leading edge (204), and a trailing edge (206). The airfoil portion is twisted in a radial direction from the airfoil base end to the airfoil tip end. The airfoil portion includes a first void (220) between the concave side exterior surface and the convex side exterior surface and extending radially to define the shape of a rib of an airfoil to be cast around the core. A first leading edge surface and a first trailing edge surface of the void are twisted from the airfoil base end to the airfoil tip end.

Abstract translation: 一种用于扭转燃气涡轮发动机叶片的铸造芯（200），包括：机翼部分（202），其具有：翼型基端（208），翼型末端（210），凹侧外表面（212）， 凸起侧外表面（214），前缘（204）和后缘（206）。 翼型部分从翼型件底端到翼型件末端的径向扭转。 翼型部分包括在凹侧外表面和凸侧外表面之间的第一空隙（220），并且径向延伸以限定要围绕芯体铸造的翼型肋的形状。 空隙的第一前缘表面和第一后缘表面从翼型件基端扭转到翼型件末端。

公开(公告)号：US20140123675A1

公开(公告)日：2014-05-08

申请号：US13670615

申请日：2012-11-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Brian H. Terpos ,  Dustan M. Simko

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01D5/088 ,  F01D21/00 ,  F01D25/12 ,  F05D2270/3032

Abstract: An air injection system for use in a gas turbine engine includes at least one outlet port through which air is extracted from the engine only during less than full load operation, at least one rotor cooling pipe, which is used to inject the air extracted from the outlet port(s) into a rotor chamber, a piping system that provides fluid communication between the one outlet port(s) and the rotor cooling pipe(s), a blower system for extracting air from the engine through the outlet port(s) and for conveying the extracted air through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent air from passing through the piping system, and open during less than full load engine operation to allow air to pass through the piping system.

Abstract translation: 一种用于燃气涡轮发动机的空气喷射系统包括至少一个出口，通过该出口，空气仅在少于满载运行期间从发动机中抽出，至少一个转子冷却管，用于将从 出口到转子室，在一个出口和转子冷却管之间提供流体连通的管道系统，用于通过出口从发动机中提取空气的鼓风机系统， 并且将提取的空气通过管道系统和转子冷却管输送到转子室中，以及阀系统。 在全负荷发动机运行期间，阀门系统关闭，以防止空气通过管道系统，并在小于满载发动机运行期间打开以允许空气通过管道系统。

公开(公告)号：US20140123657A1

公开(公告)日：2014-05-08

申请号：US13670788

申请日：2012-11-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Vincent P. Laurello ,  Abdullatif M. Chehab ,  David A. Kemp ,  John A. Fussner ,  Yan Yin ,  Bijay K. Sultanian ,  Weidong Cai

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Vincent P. Laurello ,  Abdullatif M. Chehab ,  David A. Kemp ,  John A. Fussner ,  Yan Yin ,  Bijay K. Sultanian ,  Weidong Cai

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F01D5/088 ,  F01D21/00 ,  F01D25/12 ,  F01D25/34 ,  F05D2270/3032

Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.

Abstract translation: 用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统 在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。 在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。

公开(公告)号：US08608443B2

公开(公告)日：2013-12-17

申请号：US12813602

申请日：2010-06-11

Applicant: Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

Inventor： Ching-Pang Lee ,  Jae Y. Um ,  Mrinal Munshi ,  Humberto A. Zuniga

IPC: F01D9/06 ,  F01D5/18

CPC classification number: F01D5/186 ,  F01D5/288 ,  F01D25/12 ,  F05D2230/10 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/502 ,  F23R2900/03042 ,  Y10T29/49236

Abstract: A component wall in a turbine engine. The component wall includes a substrate, a trench, and a plurality of cooling passages. The substrate has a first surface and a second surface opposed from the first surface. The trench is located in the second surface and is defined by a bottom surface between the first and second surfaces, a first sidewall, and a second sidewall spaced from the first sidewall. The first sidewall extends radially outwardly continuously from the bottom surface of the trench to the second surface. The first sidewall includes a plurality of first protuberances extending toward the second sidewall. The cooling passages extend through the substrate from the first surface to the bottom surface of the trench. Outlets of the cooling passages are arranged within the trench such that cooling air exiting the cooling passages is directed toward respective ones of the first protuberances.

Abstract translation: 涡轮发动机中的部件壁。 部件壁包括基板，沟槽和多个冷却通道。 基板具有与第一表面相对的第一表面和第二表面。 沟槽位于第二表面中，并且由第一和第二表面之间的底表面，第一侧壁和与第一侧壁间隔开的第二侧壁限定。 第一侧壁从沟槽的底表面连续径向向外延伸到第二表面。 第一侧壁包括朝向第二侧壁延伸的多个第一突起。 冷却通道从沟槽的第一表面延伸到底表面。 冷却通道的出口布置在沟槽内，使得离开冷却通道的冷却空气被引向第一突起中的相应的一个。

公开(公告)号：US08500396B2

公开(公告)日：2013-08-06

申请号：US11507120

申请日：2006-08-21

Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

公开(公告)号：US08435001B2

公开(公告)日：2013-05-07

申请号：US12640242

申请日：2009-12-17

Applicant: Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

Inventor： Matthew D. Montgomery ,  Ching-Pang Lee ,  Chander Prakash

IPC: F01D9/00

CPC classification number: F01D5/145 ,  F05D2270/172 ,  Y02T50/67 ,  Y02T50/673

Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.

Abstract translation: 翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46） 翼型的跨跨区域。 这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。 等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。 等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

公开(公告)号：US08425183B2

公开(公告)日：2013-04-23

申请号：US11602421

申请日：2006-11-20

Applicant: Ching-Pang Lee ,  Kevin Samuel Klasing ,  Paul Hadley Vitt ,  Brian David Keith

Inventor： Ching-Pang Lee ,  Kevin Samuel Klasing ,  Paul Hadley Vitt ,  Brian David Keith

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/70 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.

Abstract translation: 涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。 末端肋在翼型件的前缘和后缘之间间隔开，以包括限定三腔尖端腔的三尖头挡板。

公开(公告)号：US20130017080A1

公开(公告)日：2013-01-17

申请号：US13212273

申请日：2011-08-18

Applicant: Kok-Mun Tham ,  Ching-Pang Lee

Inventor： Kok-Mun Tham ,  Ching-Pang Lee

IPC: F01D9/02

CPC classification number: F01D5/145 ,  F01D5/143 ,  F05D2240/80

Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.

Abstract translation: 在燃气涡轮发动机中，导流构件包括支撑在转子上的平台，径向面向的端壁，从与端壁的接合处径向向内延伸的至少一个轴向表面，从端壁径向向外延伸的翼型件和流体 流导向功能。 流体流动导向特征包括沿轴向延伸并且具有径向内部和外部凹槽端部的凹槽。 外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成用于将冷却流体引导到端壁的开口。 所述凹槽还包括从所述内槽端延伸到所述外槽端部的第一槽壁和与所述第一槽壁相对并从所述内槽端部延伸到所述外槽端部的第二槽壁。

公开(公告)号：US20120282108A1

公开(公告)日：2012-11-08

申请号：US13099521

申请日：2011-05-03

Applicant: Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

Inventor： Ching-Pang Lee ,  Shantanu P. Mhetras ,  Glenn E. Brown

IPC: F01D5/18

CPC classification number: F01D5/20

Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Abstract translation: 公开了一种从压力侧肋和从涡轮叶片的尖端径向向外延伸的吸力侧肋形成的尖叫尖端。 压力和吸力侧肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力和吸力侧肋可以包括倒角的前缘，其中膜冷却孔具有位于其中的排气口。 膜冷却孔可以被配置为具有一个或多个锥形部分的扩散冷却孔，用于降低冷却流体的速度并增加对流表面的尺寸。